SATELLITE BOOST PHASE HEATING,
Abstract
An analytical and experimental study of boost phase heating of satellite 1963 22A has been accomplished. Two stages of heating were considered: (1) Radiative and convective heat transfer between heat shield and payload, and (2) Direct aerodynamic heating after heat shield ejection. The results show that a maximum temperature rise possible on any portion of the payload is 38 degrees F before heat shield ejection and about 240 degrees F after heat shield ejection. However, the latter temperature rise is highly localized and the associated heat input is easily accommodated by the payload without any perceptible overall temperature increase. It was concluded that, for the contemplated boost trajectory, no serious heating of the satellite would be encountered. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Mar 12, 1964
- Accession Number
- AD0622484
Entities
People
- R. M. Vernon
Organizations
- Johns Hopkins University Applied Physics Laboratory